Numerical–experimental investigation on post-buckled stiffened composite panels

The present work deals with a numerical–experimental investigation into the post-buckling behavior of two demonstrators representative of the bottom skin panel of an unpressurized aircraft fuselage: one represents an undamaged reference structure, the other includes debonding and impact damage. Tests have been developed for static compression loading up to the ultimate load. The recorded data from five transducers and one strain gauge have been utilized to obtain numerical–experimental correlation. Numerical analyses have been developed using two available commercial codes and by different modeling approaches and analytical procedures. Further results have been obtained and compared with each other and with experimental evidence in order to assess the capability and feasibility of numerical predictions in the post-buckling field.